38608 Federal Register / Vol. 86, No. 138 / Thursday, July 22, 2021 / Proposed Rules 

DATES: The period for completion of the 

review of the subject residential 

mortgage provisions and publication of 

notice disclosing the determination of 

this review is extended until December 

20, 2021. Notice of the commencement 

of the review was published on 

December 20, 2019 (84 FR 70073), and 

notice of the extension of the review 

and of publication of the determination 

was published on June 30, 2020 (85 FR 

39099). 

FOR FURTHER INFORMATION CONTACT: 

OCC: Daniel Borman, Counsel, or 

Kevin Korzeniewski, Counsel, Chief 

Counsel’s Office, (202) 649–5490; Maria 

Gloria Cobas, (202) 649–5495, Senior 

Financial Economist, Office of the 

Comptroller of the Currency, 400 7th 

Street SW, Washington, DC 20219. 

Board: Flora H. Ahn, Special Counsel, 

(202) 452–2317, David W. Alexander, 

Senior Counsel, (202) 452–287, or 

Matthew D. Suntag, Senior Counsel, 

(202) 452–3694, Legal Division; Sean 

Healey, Lead Financial Institution 

Policy Analyst, (202) 912–4611, 

Division of Supervision and Regulation; 

Karen Pence, Deputy Associate Director, 

Division of Research & Statistics, (202) 

452–2342; Nikita Pastor, Senior 

Counsel, Division of Consumer & 

Community Affairs (202) 452–3692; 

Board of Governors of the Federal 

Reserve System, 20th and C Streets NW, 

Washington, DC 20551. 

FDIC: Rae-Ann Miller, Senior Deputy 

Director, (202) 898–3898; Kathleen M. 

Russo, Counsel, (703) 562–2071, 

krusso@fdic.gov; Phillip E. Sloan, 

Counsel, (202) 898–8517, psloan@

fdic.gov, Federal Deposit Insurance 

Corporation, 550 17th Street NW, 

Washington, DC 20429. 

Commission: Arthur Sandel, Special 

Counsel; Kayla Roberts, Special 

Counsel; Katherine Hsu, Chief, (202) 

551–3850, in the Office of Structured 

Finance, Division of Corporation 

Finance; or Chandler Lutz, Economist, 

(202) 551–6600, in the Office of Risk 

Analysis, Division of Economic and 

Risk Analysis, U.S. Securities and 

Exchange Commission, 100 F Street NE, 

Washington, DC 20549. 

FHFA: Ron Sugarman, Principal 

Policy Analyst, Office of Capital Policy, 

(202) 649–3208, Ron.Sugarman@

fhfa.gov, or Peggy K. Balsawer, 

Associate General Counsel, Office of 

General Counsel, (202) 649–3060, 

Peggy.Balsawer@fhfa.gov, Federal 

Housing Finance Agency, Constitution 

Center, 400 7th Street SW, Washington, 

DC 20219. The telephone number for 

the Telecommunications Device for the 

Deaf is (800) 877–8339. 

HUD: Kurt G. Usowski, Deputy 

Assistant Secretary for Economic 

Affairs, U.S. Department of Housing & 

Urban Development, 451 7th Street SW, 

Washington, DC 20410; telephone 

number 202–402–5899 (this is not a tollfree number). Persons with hearing or 

speech impairments may access this 

number through TTY by calling the tollfree Federal Relay at 800–877–8339. 

SUPPLEMENTARY INFORMATION: The credit 

risk retention regulations are codified at 

12 CFR part 43; 12 CFR part 244; 12 CFR 

part 373; 17 CFR part 246; 12 CFR part 

1234; and 24 CFR part 267 (the Credit 

Risk Retention Regulations). The Credit 

Risk Retention Regulations require the 

OCC, Board, FDIC and Commission, in 

consultation with FHFA and HUD, to 

commence, and give notice of 

commencement of, a review of the 

following provisions of the Credit Risk 

Retention Regulations no later than 

December 24, 2019: (1) The definition of 

qualified residential mortgage (QRM) in 

section l.13 of the Credit Risk 

Retention Regulations; (2) the 

community-focused residential 

mortgage exemption in section l.19(f) 

of the Credit Risk Retention Regulations; 

and (3) the exemption for qualifying 

three-to-four unit residential mortgage 

loans in section l.19(g) of the Credit 

Risk Retention Regulations (collectively, 

the ‘‘subject residential mortgage 

provisions’’). The Credit Risk Retention 

Regulations also require that, after 

completion of this review, but no later 

than six months after publication of the 

notice announcing the review, unless 

extended by the agencies, the agencies 

publish a notice disclosing the 

determination of their review. 

The agencies published a notification 

announcing the commencement of the 

review in the Federal Register on 

December 20, 2019 (84 FR 70073). The 

agencies published a notification 

announcing their decision to extend to 

June 20, 2021, the period for completion 

of the review and publication of 

notification disclosing the 

determination of the review, in the 

Federal Register on June 30, 2020 (85 

FR 39099). 

The agencies are providing 

notification that the agencies have 

extended the period for completion of 

their review of the subject residential 

mortgage provisions and publication of 

the notice disclosing a determination of 

this review until December 20, 2021. 

Michael J. Hsu, 

Acting Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System acting through the 

Secretary of the Board under delegated 

authority. 

Ann E. Misback, 

Secretary of the Board. 

Federal Deposit Insurance Corporation. 

Dated at Washington, DC, on July 6, 2021. 

James P. Sheesley, 

Assistant Executive Secretary. 

Dated: July 6, 2021. 

By the Securities and Exchange 

Commission. 

J. Matthew DeLesDernier, 

Assistant Secretary. 

Sandra L. Thompson, 

Acting Director, Federal Housing Finance 

Agency. 

By the Department of Housing and Urban 

Development. 

Lopa P. Kolluri, 

Principal Deputy Assistant Secretary for 

Housing, Federal Housing Commissioner. 

[FR Doc. 2021–15424 Filed 7–21–21; 8:45 am] 

BILLING CODE 4810–33–P; I210–01–P; 6714–01–P; 8070– 

01–P; 8011–01–P; 4210–67–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0197; Project 

Identifier 2018–SW–107–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

Airbus Helicopters Model EC 155B and 

EC155B1 helicopters. This proposed AD 

would require replacing the main 

gearbox (MGB), or as an alternative, 

replacing the epicyclic reduction gear 

module for certain serial numbered 

planet gear assemblies installed on the 

MGB. This proposed AD would also 

require inspecting the MGB magnetic 

plugs, MGB filter, and oil sump for 

particles. Depending on the outcome of 

these inspections, this proposed AD 

would require further inspections and 

replacing certain parts. This proposed 

AD would also prohibit installing 

certain parts. This proposed AD was 

prompted by the failure of an MGB 

second stage planet gear. The actions of 

this proposed AD are intended to 

correct an unsafe condition on these 

helicopters. 


lotter on DSK11XQN23PROD with PROPOSALS1
Federal Register / Vol. 86, No. 138 / Thursday, July 22, 2021 / Proposed Rules 38609 

DATES: The FAA must receive comments 

on this proposed AD by September 7, 

2021. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

https://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: (202) 493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed rule, contact Airbus 

Helicopters, 2701 North Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

the referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0197; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this NPRM, the 

European Aviation Safety Agency (now 

European Union Aviation Safety 

Agency) (EASA) AD, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aerospace Engineer, 

Dynamic Systems Section, Technical 

Innovation Policy Branch, Policy & 

Innovation Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–0197; Project Identifier 

2018–SW–107–AD’’ at the beginning of 

your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Rao Edupuganti, 

Aerospace Engineer, Dynamic Systems 

Section, Technical Innovation Policy 

Branch, Policy & Innovation Division, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email rao.edupuganti@faa.gov. 

Any commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0263, 

dated December 7, 2018 (EASA AD 

2018–0263), to correct an unsafe 

condition for Airbus Helicopters Model 

EC 155 B and EC 155 B1 helicopters. 

EASA advises that after an accident on 

a Model EC225 helicopter, an 

investigation revealed the failure of an 

MGB second stage planet gear. EASA 

states that one of the two types of planet 

gear used in the MGB epicyclic module 

is subject to higher outer race contact 

pressures and therefore is more 

susceptible to spalling and cracking. 

EASA AD 2018–0263 consequently 

requires repetitive inspections of the 

MGB magnetic plugs, the MGB filer, and 

the oil sump for particles, and 

depending on the results of those 

inspections, removing or replacing 

certain parts. EASA AD 2018–0263 also 

requires reducing the life limit of Type 

Z planet gear assemblies. EASA AD 

2018–0263 also requires, if certain gear 

assemblies are installed, either replacing 

the MGB or replacing the epicyclic 

reduction gear. Finally EASA AD 2018– 

0263 prohibits installing a Type Y 

planet gear assembly or an MGB with a 

Type Y planet gear assembly on any 

helicopter. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA of the unsafe condition described 

in its AD. The FAA is proposing this AD 

after evaluating all known relevant 

information and determining that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type designs. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin ASB No. EC155– 

05A034, Revision 5, dated December 4, 

2018 (ASB EC155–05A34 Rev 5) for 

Model EC 155 helicopters, which 

specifies periodic inspections of the 

MGB magnetic plugs, the MGB filter, 

and the oil sump for particles. ASB 

EC155–05A34 Rev 5 also specifies 

identifying the type of gear assembly 

installed in the MGB and replacing any 

Type Y planet gear assembly within 50 

hours time-in-service (TIS). For Type Z 

gear assemblies that have logged less 

than 1,800 hours TIS since new, this 

service information specifies replacing 

the gear assembly before exceeding 

1,800 total hours TIS, and for Type Z 

gear assemblies that have logged 1,800 

or more total hours TIS, replacing the 

gear assembly within 600 hours TIS. 

The FAA also reviewed Airbus 

Helicopters Service Bulletin SB No. 

EC155–63–016, Revision 4, dated July 

26, 2018, for Model EC 155 helicopters. 

This service information specifies 

procedures for replacing the MGB 

epicyclic reduction gear without 

removing the MGB. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 


lotter on DSK11XQN23PROD with PROPOSALS1
38610 Federal Register / Vol. 86, No. 138 / Thursday, July 22, 2021 / Proposed Rules 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require for 

helicopters with at least one Type Y 

planet gear assembly with a certain 

serial number (S/N) installed, or at least 

one Type Z planet gear assembly with 

a certain S/N installed, within 10 hours 

TIS after the effective date of this AD 

and thereafter at intervals not to exceed 

10 hours TIS, inspecting the MGB 

magnetic plugs for particles. If there are 

particles, the proposed AD would 

require further inspections and 

analyses, and replacing the MGB, 

depending on the type and the size of 

the particles. 

This proposed AD would also require 

for helicopters with a Type Y planet 

gear assembly with a certain S/N 

installed, within 25 hours TIS after the 

effective date of this AD, inspecting the 

MGB filter for particles. If there are 

particles, this proposed AD would 

require further inspections and 

analyses, and replacing the MGB, 

depending on the type and the size of 

the particles. This proposed AD would 

require for helicopters with at least one 

Type Y planet gear assembly with a 

certain S/N installed, within 50 hours 

TIS after the effective date of this AD, 

replacing the MGB. As an alternative to 

replacing the MGB, this proposed AD 

would allow replacing the epicyclic 

reduction gear in the affected MGB. 

Additionally, this proposed AD 

would require, for helicopters without 

any Type Y planet gear assembly but at 

least one Type Z planet gear assembly 

with a certain S/N installed, replacing 

the MGB within 50 hours TIS after the 

effective date of this AD or before any 

planet gear assembly accumulates 1,800 

total hours TIS, whichever occurs later. 

As an alternative to replacing the MGB, 

this proposed AD would allow replacing 

the epicyclic reduction gear in the 

affected MGB. 

This proposed AD would require, for 

helicopters with at least one Type Z 

planet gear with a certain S/N installed, 

within certain compliance times 

specified in the figures in this AD, 

inspecting the MGB filter and inspecting 

the oil sump for particles. If there are 

particles this proposed AD would 

require further inspections and 

analyses, and replacing the MGB, 

depending on the type and the size of 

the particles. 

This proposed AD would prohibit 

installing an MGB with a certain serial 

numbered Type Y planet gear assembly 

and this proposed AD would also 

prohibit installing a Type Y planet gear 

assembly with a certain S/N on any 

helicopter. 

This proposed AD would also 

prohibit installing certain serial 

numbered Type Z planet gear 

assemblies that have accumulated 1,800 

or more total hours TIS and prohibit 

installing an MGB with certain serial 

numbered Type Z planet gear 

assemblies that have accumulated 1,800 

or more total hours TIS. 

Finally, this proposed AD would 

prohibit installing an MGB if the type of 

the planet gear assembly cannot be 

determined and would also prohibit 

installing any planet gear assembly if 

the type cannot be determined. 

Differences Between This Proposed AD 

and the EASA AD 

EASA AD 2018–0263 specifies 

compliance times based on flight hours 

and calendar dates. This proposed AD 

would set compliance times based on 

hours TIS or before further flight. EASA 

AD 2018–0263 allows a pilot to inspect 

the MGB magnetic plugs for particles, 

while this proposed AD would not. For 

helicopters with at least one affected 

Type Z planet gear assembly that has 

accumulated 1,800 or more total hours 

TIS installed, EASA AD 2018–0263 

requires replacing the MGB or epicyclic 

reduction gear within 600 flight hours 

after March 16, 2018, whereas this 

proposed AD would require either of 

those replacements within 50 hours TIS 

after the effective date of this proposed 

AD instead. If 16NCD13 particles are 

present, EASA AD 2018–0263 requires 

taking a 1 liter sample of oil and 

returning it to Airbus Helicopters and 

removing the MGB for depot-level 

inspection, whereas this proposed AD 

would require replacing the MGB 

instead. 

Interim Action 

The FAA considers this proposed AD 

to be an interim action. If final action is 

later identified, the FAA might consider 

further rulemaking then. 

Costs of Compliance 

The FAA estimates that this proposed 

AD would affect 14 helicopters of U.S. 

Registry. The FAA estimates that 

operators may incur the following costs 

in order to comply with this proposed 

AD. Labor costs are estimated at $85 per 

work-hour. 

Inspecting the magnetic plugs for 

particle deposits would take about 1 

work-hour for an estimated cost of $85 

per helicopter per inspection cycle. 

Inspecting the MGB filter and oil 

sump for particle deposits would take 

about 1 work-hour for an estimated cost 

of $85 per helicopter per inspection 

cycle. 

Replacing an MGB would take about 

42 work-hours, and parts would cost 

about $295,000 (overhauled) for an 

estimated total cost of $298,570 per 

helicopter. 

Replacing the epicyclic reduction gear 

would take about 56 work-hours and 

parts would cost about $11,404 for an 

estimated total cost of $16,164 per 

helicopter. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Would not affect intrastate aviation 

in Alaska, and 

3. Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


lotter on DSK11XQN23PROD with PROPOSALS1
Federal Register / Vol. 86, No. 138 / Thursday, July 22, 2021 / Proposed Rules 38611 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

Airbus Helicopters: Docket No. FAA–2021– 

0197; Project Identifier 2018–SW–107– 

AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by September 7, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC 155B and EC155B1 helicopters, 

certificated in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300, Main Rotor Drive System. 

(e) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a main gearbox (MGB) planet gear 

assembly. This condition could result in 

failure of the MGB and subsequent loss of 

helicopter control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For helicopters with at least one Type 

Y planet gear assembly with a serial number 

(S/N) listed in Appendix 4.A. of Airbus 

Helicopters Alert Service Bulletin ASB No. 

EC155–05A034, Revision 5, dated December 

4, 2018 (ASB EC–155–05A034 Rev 5) or with 

at least one Type Z planet gear assembly with 

an S/N listed in Appendix 4.B. of ASB 

EC155–05A034 Rev 5 installed, within 10 

hours time-in-service (TIS) after the effective 

date of this AD, and thereafter at intervals not 

to exceed 10 hours TIS, inspect the MGB 

magnetic plugs for particles. If there are any 

particles that consist of any scale, flake, 

splinter, or other particle other than cotter 

pin fragments, pieces of lock wire, swarf, 

abrasion, or miscellaneous non-metallic 

waste, and any of the planet gears have 

accumulated less than 50 total hours TIS, 

before further flight, inspect the MGB filter 

and oil sump for particles. Thereafter, for 25 

hours TIS, continue to inspect the MGB plugs 

for particles before each flight, inspect the 

MGB filter and oil sump for particles at 

intervals not to exceed 25 hours TIS, and 

inspect the cumulative surface area of the 

particles collected from the magnetic plugs, 

the MGB filter, and the oil sump, since last 

MGB overhaul, or since new if no overhaul 

has been performed. 

Note to paragraph (g)(1): Airbus 

Helicopters service information refers to an 

MGB filter as an oil filter. 

(i) If the total surface area of the particles 

is less than 3 mm2, examine the particles 

with the largest surface area (S), greatest 

length (L), and greatest thickness (e). 

(A) If any (S) of all of the particles is less 

than or equal to 1 mm2, the (L) is less than 

or equal to 1.5 mm, and the (e) is less than 

or equal to 0.2 mm, inspect the MGB plugs 

for particles before further flight, and inspect 

the MGB filter and oil sump for particles 

within 25 hours TIS. Thereafter: 

(1) For 25 hours TIS, continue to inspect 

the MGB plugs for particles before each flight 

and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(2) Inspect the MGB filter and oil sump for 

particles at intervals not to exceed 25 hours 

TIS and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(B) If any (S) is greater than 1 mm2, (L) is 

greater than 1.5 mm, or (e) is greater than 0.2 

mm, perform a metallurgical analysis for any 

16NCD13 particles, using a method in 

accordance with FAA-approved procedures. 

(C) If there are any 16NCD13 particles, 

before further flight, replace the MGB with an 

airworthy MGB. 

(D) If there are no 16NCD13 particles, 

inspect the MGB plugs for particles before 

further flight and inspect the MGB filter and 

oil sump for particles within 25 hours TIS. 

Thereafter: 

(1) For 25 hours TIS, continue to inspect 

the MGB plugs for particles before each flight 

and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(2) Inspect the MGB filter and oil sump for 

particles at intervals not to exceed 25 hours 

TIS and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(ii) If the total surface area of collected 

particles is greater than or equal to 3 mm2, 

before further flight, perform a metallurgical 

analysis for any 16NCD13 particles using a 

method in accordance with FAA-approved 

procedures. 

(A) If there are any 16NCD13 particles, 

before further flight, replace the MGB with an 

airworthy MGB. 

(B) If there are no 16NCD13 particles, 

inspect the MGB plugs for particles before 

further flight and inspect the MGB filter and 

oil sump for particles within 25 hours TIS. 

Thereafter: 

(1) For 25 hours TIS, continue to inspect 

the MGB plugs for particles before each flight 

and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(2) Inspect the MGB filter and oil sump for 

particles at intervals not to exceed 25 hours 

TIS and perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 

(2) For helicopters with at least one Type 

Y planet gear assembly with an S/N listed in 

Appendix 4.A. of ASB EC–155–05A034 Rev 

5 installed, within 25 hours TIS after the 

effective date of this AD, inspect the MGB 

filter for particles. If there are any particles 

that consist of any scale, flake, splinter, or 

particle other than cotter pin fragments, 

pieces of lock wire, swarf, abrasion, or 

miscellaneous non-metallic waste, and any of 

the planet gears have accumulated more than 

50 total hours TIS, before further flight, 

perform the actions required by paragraphs 

(g)(1)(i) and (ii) of this AD. 

(3) For helicopters with at least one Type 

Y planet gear assembly with an S/N listed in 

Appendix 4.A. of ASB EC–155–05A034 Rev 

5 installed, within 50 hours TIS after the 

effective date of this AD, replace the MGB or 

as an alternative to replacing an affected 

MGB, replace the epicyclic reduction gear 

module in the affected MGB in accordance 

with paragraph 3.B.2. of the Accomplishment 

Instructions of Airbus Helicopters Service 

Bulletin SB No. EC155–63–016, Revision 4, 

dated July 26, 2018 (SB EC155–63–016 Rev 

4), except you are not required to contact 

Airbus Helicopters. 

(4) For helicopters without any Type Y 

planet gear assembly installed but with at 

least one Type Z planet gear assembly with 

an S/N listed in Appendix 4.B. of ASB 

EC155–05A034 Rev 5 installed, within 50 

hours TIS after the effective date of this AD, 

or before any gear accumulates 1,800 total 

hours TIS, whichever occurs later, replace 

the MGB or as an alternative to replacing an 

affected MGB, replace the epicyclic reduction 

gear module in the affected MGB in 

accordance with paragraph 3.B.2. of the 

Accomplishment Instructions of SB EC155– 

63–016 Rev 4, except you are not required to 

contact Airbus Helicopters. 

(5) For helicopters with at least one Type 

Z planet gear assembly with an S/N listed in 

Appendix 4.B. of ASB EC155–05A034 Rev 5 

installed, inspect the MGB filter for particles 

within the compliance times specified in 

Figure 1 to paragraph (g)(5) of this AD and 

inspect the oil sump for particles within the 

compliance times specified in Figure 2 to 

paragraph (g)(5) of this AD, based on the total 

hours TIS accumulated by the Type Z planet 

gear with the most total hours TIS 

accumulated since first installation in an 

MGB. If there are particles, before further 

flight, perform the actions required by 

paragraphs (g)(1)(i) and (ii) of this AD. 


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38612 Federal Register / Vol. 86, No. 138 / Thursday, July 22, 2021 / Proposed Rules 

(6) As of the effective date of this AD, do 

not install a type Y planet gear assembly with 

an S/N listed in Appendix 4.A. of ASB 

EC155–05A034 Rev 5 on any helicopter, and 

do not install an MGB with a Type Y planet 

gear assembly with an S/N listed in 

Appendix 4.A. of ASB EC155–05A034 Rev 5 

on any helicopter. 

(7) As of the effective date of this AD, do 

not install a Type Z planet gear assembly 

with an S/N listed in Appendix 4.B. of ASB 

EC155–05A034 Rev 5 that has accumulated 

1,800 or more total hours TIS on any 

helicopter, and do not install an MGB with 

at least one Type Z planet gear assembly with 

an S/N listed in Appendix 4.B. of ASB 

EC155–05A034 Rev 5 that has accumulated 

1,800 or more total hours TIS on any 

helicopter. 

(8) As of the effective date of this AD, do 

not install any planet gear on any helicopter 

if the planet gear assembly type cannot be 

determined, and do not install any MGB on 

any helicopter if any of the planet gear 

assembly types cannot be determined. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (i)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

(1) For more information about this AD, 

contact Rao Edupuganti, Aerospace Engineer, 

Dynamic Systems Section, Technical 

Innovation Policy Branch, Policy & 

Innovation Division, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5110; email rao.edupuganti@

faa.gov. 

(2) For service information identified in 

this AD, contact Airbus Helicopters, 2701 

North Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. 

(3) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2018–0263, dated December 7, 

2018. You may view the EASA AD on the 

internet at https://www.regulations.gov in the 

AD Docket. 

Issued on July 14, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–15477 Filed 7–21–21; 8:45 am] 

BILLING CODE 4910–13–P 


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Total Hours TIS Compliance Time for Compliance Time for 

Accumulated Initial Ins ection Re etitive Ins ections 

ess than 400 total hours TIS ithin 55 hours TIS after the ithin 55 hours TIS 

ffective date of this AD 

00 or more total hours TIS ithin 25 hours TIS after the ithin 25 hours TIS 

Total Hours TIS 

Accumulated 

ffective date of this AD 

Figure 1 to Paragraph (g)(5) 

Compliance Time for 

Initial Ins ection 

Compliance Time for 

Re etitive Ins ections 

ess than 400 total hours TIS efore exceeding 400 hours ithin 55 hours TIS 

00 or more total hours TIS 

IS after the effective date o 

ithin 55 hours TIS after the ithin 55 hours TIS 

ffective date of this AD 

Figure 2 to Paragraph (g)(5)